Aircraft with a plurality of propellers, a pipe structure for thereon holdable wings for vertical take off and landing

Abstract

An aircraft has a pair of wing portions with propellers of a propeller pair which are driven and synchronized by a fluid transmission between the power plant and the propellers. A fluid line structure keeps most components of the craft together and consists preferredly of three pipes which are also utilized to carry the driving fluid to and from the motors, to hold the motors and to hold the wings. The take over of a plurality of functions by the interior pipe structure reduces weight and secures safe and economic operation of the craft. The pipe structure can be pivoted in respective bearings to effect the pivotal movement of the propellers and wing portions for either vertical take off and landing or horizontal flight. The pipe structure is built by pipes without bends in order to make the cleaning of the interiors of the pipes from dirt and remainders of weldings possible. Ribs and holding portions are provided on the structure for assembly and/or disassembly of the wing portions to the pipe structure.

What is claimed is: 
     
       1. An aircraft, which comprises, in combination, a body, at least one power plant, at least four propellers, at least two pairs of wing portions, a transmission between said power plant and said propellers with said transmission leading equal portions of power from said power plant to said propellers, whereby said transmission transfers at least four portions of equal power and rate of speed individually each one of said portions of power individually to one of said propellers to synchronize the rotary velocities of said four propellers to equal speeds and forces arrangements to pivot the axes of said propellers and of said wing portions from vertical to horizontal and vice versa in unison and and improvement,   wherein said improvement comprises, in combination, arrangements in said power plant and in said transmission,   wherein said power plant revolves an output shaft in excess of three thousand revolutions per minute,   wherein said transmission includes a horizontal shaft in said body with a first tapered gear, one front first gear and a rear first gear on the respective end of said shaft,   wherein a vertical shaft with second and third tapered gears on its ends is provided in said body,   wherein a lateral shaft with fourth and fifth tapered gears on its end is provided laterally extending from said body and extending into a wing portion of said wing portions,   wherein a propeller driving shaft is provided with a sixth tapered gear in said wing portion and with holding means to hold a propeller,   wherein said first gear engages and meshes with said second gear, said third gear engages and meshes with said fourth gear, said furth gear engages and meshes with said fifth gear and said fifth gear engages and meshes with said sixth gear,   wherein said propeller driving shaft is borne in bearings and carries said propeller to revolve said propeller,   wherein said transmission includes a second horizontal shaft with gears complementary to said gears of said first shaft,   wherein four of said horizontal shaft, four of said lateral shafts and four of said propeller driving shafts are provided each with gears equal and complementary to said described gears,   whereby said four propeller driving shafts engage and drive said four propellers over said shafts and gears, and   wherein a pair of pipe structures is pivotably provided in said body, while each of said structures consists of at least three substantially parallel pipes which carry inner and outer bearings with said structures provided with holders to hold said wing portions, and   wherein said lateral shaft is provided between portions of said pipes of said structures while said lateral shaft is borne in said inner and outer bearings.   
     
     
       2. The aircraft of claim 1, wherein every single structure of said pair of pipe structures has a medial portion inside of said body between outer portions laterally outside of said body, and,   wherein the pipe portions of said medial portion are wider distanced from each other than the pipes of said outer portions of said pipe structure.   
     
     
       3. The aircraft of claim 2, wherein said third gear is provided between said pipes of said medial portion of said pipe structure.   
     
     
       4. The aircraft of claim 1, wherein said lateral shaft is hollow, and,   wherein an independent shaft is located in and extended through said lateral shaft.   
     
     
       5. The aircraft of claim 4, wherein said independent shaft is provided with connections to ailerons which are provided on a respective portion of said wing portions and to a controller for the operation of said ailerons.   
     
     
       6. The aircraft of claim 1, wherein said shafts are pipes with an inner diameter which is substantially about 70 percent of the outer diameter of the respective shaft.